Snecma

Snecma Moteurs

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Other

Safran Aircraft Engines

Daniel Georges Plona

Guy Dusserre-Telmon

Guy Franck Dusserre-Telmon

Daniel Olivier Bainachi

Romain Nicolas Lunel

Gilles Alain Marie Charier

Gilles Alain Charier

Antoine Robert Alain Brunet

Mathieu Dakowski

Damien Joseph Cellier

Philippe Pierre Vincent Bouiller

Philippe Pierre Bouiller

Jerome M Friedel

Patrick Morel

Jean-Pierre Mourlan

Jean-Pierre Andre Joseph Mourlan

Olivier Kreder

Monique Andr&eacute;e Thore

Christophe Yvon Tourne

Mickael Dias Gomes

Jérôme Friedel

A device for damping a rolling bearing includes a support and a radially flexible cage. The cage includes a ring provided in order to be mounted on the periphery of a rolling bearing. The radial flexibility of this cage results from the structure thereof which is perforated by oblique posts connecting the ring to an attachment annulus of this cage. The support includes a plurality of teeth each extending radially through a respective inter-post opening of the cage. The ring and the support form, radially between one another, a fluid damping cavity suitable for forming a compressed fluid film. The device allows a controlled radial movement of the ring, the latter being radially limited by the support, while having a limited footprint.

Device for damping a rolling bearing, comprising a rigid support passing through a flexible cage

The main object of the invention is an angular stator sector () for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterized in that the inner shroud (S) comprises at least one brush seal () forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).

Angular stator sector for a turbomachine compressor comprising a brush seal

An annular bearing cage for a roller bearing of a turbine machine rotating shaft is provided. The bearing cage includes a vibration damping ring corresponding to deformation modes of the bearing cage, and at least one external rim. The external rim includes an at least partially annular housing that extends around a central axis of the bearing cage. The damping ring is located in the housing.

Bearing cage with a peripheral vibration damping ring

A seal capable of providing a seal for an air gap between a rotor and a stator. The seal incorporates a container for the textile insulators fixed on the rotor or the stator. The textile insulators are subjected, on one side, to an upstream pressure and, on another side, to downstream pressure, the upstream pressure being greater than the downstream pressure. The textile insulators are supported on the stator or the rotor so as to be at an angle to the side of the seal where the pressure is lower, namely the downstream pressure.

Dynamic brush seal

A bearing arrangement with rolling elements is arranged between an outer bearing race and an inner bearing race. The inner bearing race includes a first half-race fastened to the rotating shaft and a second half-race. The bearing arrangement includes a maintaining unit which maintains the two half-races together. The maintaining unit is designed to break or deform when the bearing is subjected to a misalignment or a moment above a predetermined value, so as to allow an axial displacement of the second half-race with respect to the first half-race. The invention may be applied to a bearing for a rotating shaft of a turbine engine.

Bearing arrangement for a rotating shaft, and turbine engine equipped with such an arrangement

The jet engine of the invention comprises an exhaust nozzle of variable section, comprising at least one flap pivot mounted about a pin, the pin being joined to the fixed structure of the jet engine via two braces each comprising a bore for housing the pin, the flap being pivot commanded by an actuating cylinder, connected to two fasteners which each comprise a bore through which the pin passes and about which they rotate. The jet engine is characterized by the fact that the pin, the bores of the braces and bores of the fasteners are arranged so that the contacts between the pin with the bore walls of the braces and with the bore walls of the fasteners are made over convex surfaces. Therefore, when in operation, in the event of pin bending the contact surfaces follow this convex shape and are suitably distributed.

Jet engine with a variable section nozzle of which at least one flap pivots about a pin, pins for flaps

The quality of the lubrication of an inter-shaft bearing, particularly one with counter-rotational bushes, is improved by the presence of an obstacle on the outer bush which allows an adjustment in the quantity of oil present on the outer roll track. In particular, the drying of the roll track under the effect of the repeated running of the runners is compensated for by organizing a mandatory axial circulation.

Compensation for an insufficient supply of lubricant in an inter-shaft bearing

An assembly arrangement between an inner race of a bearing and a journal supported in rotation in this bearing includes a journal annular groove and a race annular groove which interact to form an annular channel when they are placed opposite one another. The assembly further includes a retaining ring placed in the annular channel, which prevents a relative movement in translation between the journal and the inner race. The assembly also includes at least one recess of the journal and at least one tooth of the inner race, which interact to prevent a relative movement in rotation between the journal and the inner race.

Assembly arrangement between a bearing inner race and a journal, race and journal suitable for such an arrangement, and turbomachine fitted therewith

A recentering device for a rotor shaft for recentering a rotor shaft relative to an axis X of a stator structure in the event of decoupling caused by excessive imbalance. The shaft, in normal operating conditions, lies on the axis X and is radially supported by a bearing support disposed in a bore of the axis X in the stator structure. The bearing support has an outside diameter smaller than the diameter of the bore, to enable the bearing support to orbit about the axis X in the event of decoupling. The bearing support is connected to the stator structure by radially fusible elements. The recentering device recenters the bearing support after decoupling.

Rotor recentering after decoupling

A bearing assembly includes a first liquid lubricant injector designed to be fed exclusively with non-recycled liquid lubricant to lubricate a bearing. A plurality of drain orifices passes through a bearing ring fixed to a fixed part, and the assembly also includes a second liquid lubricant injector fed with liquid lubricant drained through a collection device for collecting liquid lubricant drained from the orifices, the collection device communicating firstly with a reinjection circuit connected to the second injector, and with a bypass circuit designed to evacuate surplus drained liquid lubricant.

Bearing assembly comprising double injection of liquid lubricant, and aeronautical vehicle comprising at least one such assembly

A sealing device for sealing between two static portions of a turbomachine includes a brush gasket formed by a plurality of resilient bristles which are, at least in part, held in a housing. Each bristle has a main portion and a secondary portion interconnected by a bent portion. The secondary portion has a free end ensuring leaktight contact with a surface that is to be sealed of the other static portion. The sealing device further includes a flexible washer of bent section which has a free end bearing both against the free ends of the secondary portions of the bristles of the brush gasket, and against the surface that is to be sealed so that the free ends of the secondary portions of the bristles of the brush gasket are permanently in contact with the surface that is to be sealed.

Sealing device with a brush gasket and flexible washer for a high-pressure turbine of a turbomachine

A device applied to regulating the flow rate of air flowing in a rotary shaft of a turbomachine, the shaft including at least one through orifice for passing air. The device at least one shutter member for shutting the orifice and secured to a deformable blade presenting bi-linear behavior, the blade being secured to the shaft and being suitable for deforming under the effect of the centrifugal force that results from the shaft rotating such that the shutter member is suitable for taking up two different positions depending on the speed of rotation of the shaft: one position in which it shuts the orifice; and another position in which it releases the orifice to allow air to pass through.

Method of regulating the flow rate of air in a rotary shaft of a turbomachine

A gasket, sliding about the axis of rotation of a part to be brought closer to or to be spaced apart from another part with which it provides tightness through a pair of lips provided on a ring. The gasket includes a portion of the ring capable of bending to modify the clearance between the corresponding lip and the part, the pressure prevailing in an intermediate cavity, the balance of forces on the joint and hence the clearance and the leak flow rate allowed before the gasket, which is advantageous in particular in a case of ventilation gas for refrigerating an element of the machine in controlled operating conditions.

Gasket with two concentric lips

A rolling bearing defines a separation between an oil enclosure and an air enclosure. The bearing includes rolling elements defining a first side opening and a second side opening, and includes an annular junction piece having an annular contact surface with the structural piece. An oil film is disposed at the annular contact surface between the structural piece and the junction piece and is laterally defined by at least two sealing rings. A sealing device covers at least part of the first side opening. A first oil circulation device feeds the oil film with oil and feeds the rolling elements beside the oil enclosure with oil from the oil film. A second oil circulation device, independent of the first, recovers the oil used for lubricating the rolling elements and is arranged in such a manner as to avoid oil flowing towards the air enclosure.

Oil-damped sealed rolling bearing

A rolling bearing for a turbomachine supporting a first shaft to rotate relative to a second shaft, and comprising: a plurality of rolling elements engaged between an inner annular ring mounted on the second shaft and an outer annular ring mounted on the first shaft; an oil film formed at an annular contact surface between said outer ring and said first shaft; at least one duct passing through said inner ring and opening out in an inner race for said rolling elements in order to lubricate them; and at least one additional duct passing through said inner ring and opening out outside the inner race in order to feed oil through said outer ring to said oil film under the effect of the centrifugal force generated by said second shaft rotating, said outer ring having an annular shoulder projecting radially towards the inside of said annular space, said shoulder having at least one channel opening out substantially in register with said additional duct and opening out into said oil film.

Growing community of inventors

Vulaines sur Seine, France

Daniel Georges Plona